Rotating release launching system

ABSTRACT

The present disclosure provides a payload deployment system that is operative to receive and retain a configurable payload. The payload deployment mechanism helps to reduce the drag of the payload and to protect the payload from environmental factors. The payload may be released using a hinge mechanism to ensure the payload does not contact the payload deployment mechanism when the payload is deployed. A vent may be utilized to equalize pressure between the external environment and a body portion of the payload deployment mechanism. The vent may generate an additional force to assist in separating the payload from the launcher.

RELATED APPLICATIONS

This application is a Continuation-in-Part of U.S. application Ser. No. 17/691,379 filed on Mar. 10, 2022, which is a Continuation of U.S. application Ser. No. 17/089,937 filed on Nov. 5, 2020, which issued on Jan. 4, 2022 as U.S. Pat. No. 11,214,370, which claims benefit under the provisions of 35 U.S.C. § 119(e) of U.S. Provisional Application No. 63/019,967 filed on May 4, 2020, which are incorporated herein by reference in its entirety.

It is intended that the above-referenced applications may be applicable to the concepts and embodiments disclosed herein, even if such concepts and embodiments are disclosed in the referenced applications with different limitations and configurations and described using different examples and terminology.

FIELD OF DISCLOSURE

The present disclosure relates to aviation equipment, and more specifically, to equipment that releases a payload from an aircraft.

BACKGROUND

It is often desirable to release payload from an aircraft. Indeed, aircraft release munitions, sensors, buoys, and other devices during military, scientific and public safety operations. These payloads are often attached externally on an aircraft and are exposed to environmental conditions while the aircraft operates. Such exposure may undesirably impact the flight characteristics and functionality of the payload and cause damage to the payload.

Payloads such as drones and munitions often have deployable control surfaces that extend outwardly from the body of the drone upon flight or prior to flight. A disadvantage of this arrangement is that if a drone or munition is exposed to the airflow under the wings, the flight surfaces may extend undesirably while the payload drone is still attached to the aircraft. The aircraft may also be susceptible to foreign object damage (FOD) if the payload loses a component in flight. Such an incident could cause damage to the payload or aircraft.

BRIEF OVERVIEW

This brief overview is provided to introduce a selection of concepts in a simplified form that are further described below in the detailed description. This brief overview is not intended to identify key features or essential features of the claimed subject matter. Nor is this brief overview intended to be used to limit the claimed subject matter's scope.

A rotating release launching system (also referred to herein as a “launcher”) consistent with embodiments of the present disclosure may retain a payload and provide for a “rolling” or “rotating” of the payload. The launcher may comprise a body portion; a bay area partially defined by the body portion; a door portion operative to rotate within the body portion to expose at least a portion of the bay area; and a biasing portion configured to transfer an angular momentum of the rotating door portion to the payload arranged within the door portion.

The launcher may comprise a body having a substantially tubular shape. The door portion may serve as a shuttle for the payload. The door portion may be operative to rotate in a substantially elliptical path to expose the bay area of the launcher. The bay area may be partially defined by a cavity in the body portion generated by the rotation of the door portion.

The payload may be arranged and retained within the door portion of the body. As the door portion revolves and exposes the bay area of the launcher, the payload may be released through the bay area with the angular momentum (or rotating inertia) that is generated by the door's rotation, thereby providing the rolling release of the payload out of the launcher from its bay area.

Still consistent with embodiments of the present disclosure, the door portion of the body may comprise at least one biasing and fastening mechanism. The at least one biasing and fastening mechanism may comprise, for example, but not be limited to, at least one bracket. The at least one bracket may be used to facilitate a desired alignment of the payload within the body and a desired momentum upon release from the bay area.

Accordingly, in some embodiments, the at least one biasing mechanism may comprise at least one bracket to further facilitate at least one of the following: i) the desired alignment of the payload within the body; and ii) desired release dynamics of the payload as it leaves the bay area. For example, the at least one bracket may be configured to detachably couple with at least a portion of the payload. The detachable coupling mechanism may be configured to, for example: i) retain the payload in a first orientation of the door portion, and/or ii) release the payload at a second orientation.

In the first orientation, the payload may be arranged resting within the door portion. Here, the at least one biasing mechanism may contribute to the retention of the payload's position and orientation. In a second orientation, the door portion may be rotated within the body to expose the bay area. Here, the at least one biasing mechanism may be designed to decouple the payload such that it may be released from the exposed bay area.

Accordingly, the biasing mechanism coupling the door portion with at least a portion of the payload enables a transition of the retained payload from the first orientation to the second orientation and, in turn, transfers an angular momentum to the payload as the door portion rotates within the body of the launcher to expose the bay area. Said angular momentum transferred to the payload provides for a “rolling” and “rotating” release of the payload as it exits the bay area.

In some embodiments, the door portion of the body may further comprise at least one force generating mechanism. The at least one force generating mechanism may be configured to apply a force in order to provide for at least one of the following: i) arrange the payload within the body at the first orientation, and ii) eject the payload from the bay area in the second orientation.

In the first orientation, the biasing mechanism and the force generating mechanism, according to the respective embodiments of the launcher in which they may be comprised, may enable a desired position and orientation of the payload within the body of the launcher.

In the second orientation, the biasing mechanism and the force generating mechanism, according to the respective embodiments of the launcher in which they may be comprised, may facilitate the generation of the rotating inertia as well as an added force upon the payload's release from the bay area. In this way, where the payload may be designed to expand upon a release from the launcher, such expansion may occur a greater displacement from the launcher than would otherwise occur without the additional force provided by the force generating mechanism.

The orientation of the payload may be important in various applications. For instance, in some embodiments, the payload may be an unmanned aerial vehicle designed to deploy one or more control surfaces upon release from the launcher. In such embodiments, a proper orientation of the payload, as it is released from the launcher, may provide for a more calculated expansion of its control surfaces upon release.

In some embodiments of the present disclosure, the launcher may comprise a hinge mechanism configured to control the separation of the configurable payload from the body portion of the launcher. The hinge mechanism may comprise a plurality of hinge components that together may form the hinge mechanism. Embodiments of the present disclosure may also utilize a vent on the exterior of the launcher to equalize pressure between the external environment and the body portion of the launcher, which may assist in the separation of the configurable payload from the body portion of the launcher.

Both the foregoing brief overview and the following detailed description provide examples and are explanatory only. Accordingly, the foregoing brief overview and the following detailed description should not be considered to be restrictive. Further, features or variations may be provided in addition to those set forth herein. For example, embodiments may be directed to various feature combinations and sub-combinations described in the detailed description.

BRIEF DESCRIPTION OF THE DRAWINGS

The accompanying drawings, which are incorporated in and constitute a part of this disclosure, illustrate various embodiments of the present disclosure. The drawings contain representations of various trademarks and copyrights owned by the Applicant. In addition, the drawings may contain other marks owned by third parties and are being used for illustrative purposes only. All rights to various trademarks and copyrights represented herein, except those belonging to their respective owners, are vested in and the property of the Applicant. The Applicant retains and reserves all rights in its trademarks and copyrights included herein, and grants permission to reproduce the material only in connection with reproduction of the granted patent and for no other purpose.

Furthermore, the drawings may contain text or captions that may explain certain embodiments of the present disclosure. This text is included for illustrative, non-limiting, explanatory purposes of certain embodiments detailed in the present disclosure. In the drawings:

FIG. 1 illustrates a perspective view of a launcher device;

FIG. 2 illustrates a perspective and partially exploded view of the device;

FIG. 3A illustrates a side view of the device;

FIG. 3B illustrates a side view of the device during launching process wherein a configurable payload is within the launcher;

FIG. 3C illustrates a side view of the when a force applying portion imparts a force on the configurable payload device during a launching process;

FIG. 3D illustrates a side view of the configurable payload separating from the launcher;

FIG. 3E illustrates a front view of the launcher as the configurable payload deploys from the bay area;

FIG. 4 illustrates another example embodiment of the device;

FIG. 5 illustrates a front view of a portion of the door portion;

FIG. 6 illustrates a block diagram of an example method for operation of the device;

FIG. 7 is a block diagram of a system including a computing device operable with the launcher device;

FIG. 8A illustrates a perspective view of the launcher deploying a configurable payload with a parachute utilizing the force generating mechanism;

FIG. 8B illustrates a perspective view of the parachute engaging on the configurable payload;

FIG. 9 illustrates a block diagram of an example method for deploying a payload with a parachute of the device; and

FIG. 10 illustrates a block diagram of an additional method for deploying a parachute with of the payload;

FIG. 11A illustrates a perspective view of the hinge mechanism in the stored configuration;

FIG. 11B illustrates an embodiment of a perspective view of the hinge mechanism during deployment of the configurable payload;

FIG. 11C illustrates an embodiment of a perspective view of the hinge mechanism before the configurable payload separates from the bay area of a launcher;

FIG. 12A illustrates an embodiment of a side view of the hinge mechanism in the stored configuration;

FIG. 12B illustrates an embodiment of a side view of the hinge mechanism during deployment of the configurable payload;

FIG. 12C illustrates an embodiment of a side view of the hinge mechanism before the configurable payload separates from the bay area of the launcher;

FIG. 13A illustrates an embodiment of a side view of the launcher within the configurable payload in a stored configuration using the hinge mechanism;

FIG. 13B illustrates an embodiment of a side view of the launcher during deployment of the configurable payload using the hinge mechanism;

FIG. 13C illustrates an embodiment of a side view of the launcher before the configurable payload separates from the bay area of the launcher using the hinge mechanism;

FIG. 14A illustrates an embodiment of a perspective view of the launcher within the configurable payload in a stored configuration using the hinge mechanism;

FIG. 14B illustrates an embodiment of a perspective view of the launcher during deployment of the configurable payload using the hinge mechanism; and

FIG. 14C illustrates an embodiment of a perspective view of the launcher before the configurable payload separates from the bay area of the launcher using the hinge mechanism.

DETAILED DESCRIPTION

As a preliminary matter, it will readily be understood by one having ordinary skill in the relevant art that the present disclosure has broad utility and application. As should be understood, any embodiment may incorporate only one or a plurality of the above-disclosed aspects of the disclosure and may further incorporate only one or a plurality of the above-disclosed features. Furthermore, any embodiment discussed and identified as being “preferred” is considered to be part of a best mode contemplated for carrying out the embodiments of the present disclosure. Other embodiments also may be discussed for additional illustrative purposes in providing a full and enabling disclosure. Moreover, many embodiments, such as adaptations, variations, modifications, and equivalent arrangements, will be implicitly disclosed by the embodiments described herein and fall within the scope of the present disclosure.

Accordingly, while embodiments are described herein in detail in relation to one or more embodiments, it is to be understood that this disclosure is illustrative and exemplary of the present disclosure and are made merely for the purposes of providing a full and enabling disclosure. The detailed disclosure herein of one or more embodiments is not intended, nor is to be construed, to limit the scope of patent protection afforded in any claim of a patent issuing here from, which scope is to be defined by the claims and the equivalents thereof. It is not intended that the scope of patent protection be defined by reading into any claim a limitation found herein that does not explicitly appear in the claim itself.

Thus, for example, any sequence(s) and/or temporal order of steps of various processes or methods that are described herein are illustrative and not restrictive. Accordingly, it should be understood that, although steps of various processes or methods may be shown and described as being in a sequence or temporal order, the steps of any such processes or methods are not limited to being carried out in any particular sequence or order, absent an indication otherwise. Indeed, the steps in such processes or methods generally may be carried out in various different sequences and orders while still falling within the scope of the present disclosure. Accordingly, it is intended that the scope of patent protection is to be defined by the issued claim(s) rather than the description set forth herein.

Additionally, it is important to note that each term used herein refers to that which an ordinary artisan would understand such term to mean based on the contextual use of such term herein. To the extent that the meaning of a term used herein—as understood by the ordinary artisan based on the contextual use of such term—differs in any way from any particular dictionary definition of such term, it is intended that the meaning of the term as understood by the ordinary artisan should prevail.

Regarding applicability of 35 U.S.C. § 112, ¶6, no claim element is intended to be read in accordance with this statutory provision unless the explicit phrase “means for” or “step for” is actually used in such claim element, whereupon this statutory provision is intended to apply in the interpretation of such claim element.

Furthermore, it is important to note that, as used herein, “a” and “an” each generally denotes “at least one,” but does not exclude a plurality unless the contextual use dictates otherwise. When used herein to join a list of items, “or” denotes “at least one of the items,” but does not exclude a plurality of items of the list. Finally, when used herein to join a list of items, “and” denotes “all of the items of the list.”

The following detailed description refers to the accompanying drawings. Wherever possible, the same reference numbers are used in the drawings and the following description to refer to the same or similar elements. While many embodiments of the disclosure may be described, modifications, adaptations, and other implementations are possible. For example, substitutions, additions, or modifications may be made to the elements illustrated in the drawings, and the methods described herein may be modified by substituting, reordering, or adding stages to the disclosed methods. Accordingly, the following detailed description does not limit the disclosure. Instead, the proper scope of the disclosure is defined by the appended claims. The present disclosure contains headers. It should be understood that these headers are used as references and are not to be construed as limiting upon the subjected matter disclosed under the header.

As discussed above, deploying devices such as drones, unmanned aerial vehicles, munitions, buoys or other payload from flying aircraft is challenging. If the payload is, for example, a drone mounted to the underside of an aircraft, the drone may have wings and other control surfaces that can cause drag and affect the flight characteristics of the aircraft. Furthermore, if components of the drone fall off the drone during operation, they may cause foreign object damage (FOD) to the aircraft.

Some drones have collapsible wings and control surfaces that could potentially allow such drones to be attached to the underside of an aircraft fuselage with its wings and control surfaces retracted. Such an arrangement may reduce drag on the aircraft, but it does not reduce the chances of FOD caused by the drone. The arrangement subjects the drone to the elements, which may cause the drone to malfunction. The aforementioned drone-to-aircraft attachments discussed fail to protect the drone as it may be subjected to high winds, high altitude, and a variety other environmental factors such as, for example, rain, snow, and extreme temperatures when exposed under an aircraft.

The embodiments described herein offer a launcher that is operative to receive and retain a drone or other payload and launch the payload. Accordingly, a launching enclosure may be designed to protect the drone from the elements as well as protect aircraft from potential foreign object damage caused by the system. The launcher may be configured to be installed under, for example, the fuselage, under a wing, or to another surface on an aircraft.

In some embodiments, the launcher may be configured with a rotating door. The rotating door may open to, for example, receive the payload. The door may then be closed, thereby encasing the payload in the launching assembly. Such an arrangement protects the drone from the elements. Furthermore, in embodiments in which a drone may be configured within the launcher as payload, such arrangement may also protect the aircraft from some potential consequences of having the drone mounted on the aircraft such as foreign object damage and increased drag.

In some embodiments, the launcher can be configured to deploy a payload configured with a payload drag mechanism. The payload drag mechanism may be attached to the payload or integrated into the construction of the payload. Accordingly, such a configuration can expose the payload mechanism to the elements. The exposed areas of the payload drag mechanism can be configured to provide increased protection to the elements compared to other payload areas. The payload drag mechanism may also be configured to improve the aerodynamic properties of the launcher as a whole to decrease the drag created by the launcher.

In some embodiments, the payload drag mechanism can be configured to assist in deploying the payload. For example, the payload drag mechanism can be flush with the rest of the launcher when the payload is in a first orientation. Additionally, the payload drag mechanism may assist in securing the payload within the launcher. When a force applying portion begins to transition the payload from the first configuration to the second configuration the payload drag mechanism can be exposed. The aerodynamic properties resulting from the construction of the payload drag mechanism can enable additional force generation when deployed. Upon deployment, the payload drag mechanism can utilize the additional drag to apply a force. In some embodiments, the payload drag mechanism attached to the payload creates more aerodynamic forces than a payload without the payload drag mechanism.

In some embodiments, the launcher can be configured to receive a payload partly exposed to the environment. The exposed part of the payload may be constructed to integrate with the launcher without affecting the characteristics of the launcher. Furthermore, in embodiments in which a drone may be configured within the launcher as a payload, the exposed area of the payload may be configured to protect the aircraft from some potential consequences of having the drone mounted on the aircraft, such as foreign object damage and increased drag.

The embodiments described herein can offer a configurable payload configured with a payload drag mechanism. The payload drag mechanism may be located at the forward portion of the payload. When the payload is deployed, the drag mechanism may generate an additional force on the payload. The additional force may be generated by the drag resulting from the aerodynamic properties of the payload drag mechanism. The force generated by the payload drag mechanism may increase the separation rate of the payload from the launcher or increase the potential for separation between the payload and the launcher.

Some payloads may also be configured to utilize a deployable parachute. The deployable parachute can be stored within the launcher until payload deployment. Accordingly, the parachute may be integrated into the construction of the payload or may be attached to the payload as necessary. When the payload separates from the launcher, the parachute can leave the launcher and begin deployment. Additionally, properties of the parachute can be configured to deploy based on a certain condition such as the downward velocity of the payload, time since separation from the launcher, or distance from the launcher. The payload configuration can ensure that the parachute deployment does not interfere with any other functions involved with the deployment of the payload.

Though the embodiments described herein include a drone as the payload of the launcher, the payload may include any type of device such as, for example, sensors, buoys, munitions, or any other device or object suitable for releasing from an aircraft in flight.

FIG. 1 illustrates a perspective view of a launcher 100. Launcher 100 includes a body portion 102 that is substantially tubular. Body portion 102 may be formed from, for example, but not limited to, a metallic, plastic, or composite material. A mounting portion 104 is attached to body portion 102. The mounting portion 104 is operative to attach to the aircraft, such as on pilons on an underside portion of an aircraft, such as, but not limited to, the fuselage or wings of the aircraft. The mounting portion 104 may be formed from, for example, but not limited to, a combination or metallic, plastic, and composite materials.

A nose cone 106 is arranged in a forward portion of the launcher 100. Nose cone 106 may be formed from, for example, but not be limited to, a metallic, plastic, or composite material. The launcher 100 may further comprise a door portion 108. Door portion 108 may be configured and operative to rotate about an axis of rotation. In some embodiments, the axis of rotation may be substantially parallel to the longitudinal axis 103 of launcher 100. Still consistent with embodiments of the disclosure, the axis of rotation may be substantially concentric with longitudinal axis 103.

FIG. 2 illustrates a perspective and partially exploded view of an embodiment of the launcher 100. Accordingly, in some embodiments, body portion 102 may be substantially tubular in shape and has a first distal end 201 and a second distal end 203. An electronics, sensor and control portion 204 may be located at, for example, a location proximate to the second distal end 203. The control portion 204 may comprise, for example, a drive motor that is operative to drive the opening and closing of the door portion 108, electromechanical linkages, electronic circuits, controllers and processors that may be used to operate the launcher 100 to open and close door portion 108. In some embodiments, control portion 204 may include sensors or antennas that connect to the payload (not shown). One example of some of the components that control portion 204 may comprise is illustrated and described with reference to a computing device 700 in FIG. 7 . Control portion 204 may be protected by a nose cone 106, which has an aerodynamic shape that directs airflow and reduces drag caused by launcher 100.

Launcher 100 may comprise at least one biasing and fastening mechanism. The biasing and fastening mechanism may be arranged throughout the launcher 100 and adapted to meet the form factor and other parameters associated with specific payloads. In some embodiments, door portion 108 may comprise fastening portions that assist in retaining the payload and securing the payload in the launcher 100; the fastening portions may be formed from, for example, but not limited to, metal, plastic, composite, or a mailable or compressible foam materials.

By way of non-limiting example, in a first instance, the biasing and fastening mechanisms may serve to keep the payload in a desired orientation within the payload. In another instance, the biasing and fastening mechanisms may serve to detachably couple the payload to and from the door portion 108.

Accordingly, in some embodiments, the at least one biasing and fastening mechanism may further comprise at least one bracket 202, such as the illustrated notch, to further facilitate at least one of the following: i) the desired alignment of the payload within body portion 102; and ii) a desired release dynamics of the payload out of the bay area. For example, the at least one bracket 202 may be configured to detachably couple with at least a portion of the payload. In some embodiments, an intermediary device may be used to couple the payload with the at least one bracket 202. The detachable coupling may be configured to enable a first orientation of the payload within the launcher at rest, and a second orientation of the payload within the launcher upon release. The change of orientation of the payload may correspond to the change of orientation of door portion 108 as it rotates within the launcher to expose the bay area. As will be illustrated with reference to FIGS. 3A-3E, the at least one bracket 202 may serve to transfer an angular momentum of door portion 108's rotation to the payload, thereby enabling a rolling release of the payload from launcher 100.

Furthermore, in some embodiments, launcher 100 may comprise at least one force generating mechanism 208. The force generating mechanism 208 may be used to impart a force upon the payload in the first orientation and in the second orientation. The force may serve to keep the payload at a desired position, angle, or otherwise orientation with body portion 102. For example, adjusting the location of the force generating mechanism 208 may affect the orientation of the payload within the body portion 102. Furthermore, during a launch of the payload, the force may serve to more quickly increase the separation distance between the payload and launcher 100. In some embodiments, force generating mechanism 208 may comprise any suitable type of arrangement including, for example, but not limited to, any one or more of the following: leaf springs, coil springs, or other types of arrangements operative to impart a biasing force on the payload, and may be arranged based on a type of the payload. Though the illustrated embodiment includes the force generating mechanism 208, other embodiments may exclude such components, yet still provide the technical advantages described herein.

FIGS. 3A to 3E illustrate the launching procedure of the launcher 100 as it transitions from a first orientation to a second orientation. In the illustrated example of FIG. 3A, the door portion 108 is in a fully closed position with a payload 300 in the first orientation.

In the first orientation, the payload may be arranged resting within door portion 108. In some embodiments, at least one bracket 202 may be detachable coupled to the payload in order to maintain the payload's position and orientation within launcher 100. One example of a coupling mechanism provided by at least one bracket 202 is disclosed with reference to FIG. 3E.

Referring now to FIG. 3B, the door portion 108 may be rotated about a rotational axis 303 while retaining the payload 300 such that a portion of the payload 300 is exposed. In one example, door portion 108 may be configured to rotate in a rotational direction 301, thereby providing a corresponding angular momentum in said rotational direction 301. The angular momentum may be transferred, by way of the coupling mechanism, to payload 300, thereby causing payload 300 to rotate along with door portion 108.

In some embodiments, the rotational axis 303 of door portion 108 may be approximately parallel to the longitudinal axis 103 of the launcher 100, with the rotational direction 301 approximately concentric with body 102. In other example embodiments, the door portion 108 may be may be arranged such that the door rotates about an axis (e.g., a shaft and bearing) that is offset from a central longitudinal axis 103.

FIG. 3C illustrates a side view of the launcher 100 where the door portion 108 (shown in FIG. 3B) is in a fully open position exposing the payload 300 in a bay area 310 of the launcher 100. Here, payload 300 and door portion 108 may be arranged in the second orientation.

In the second orientation, door portion 108 may be rotated within body 102 to expose the bay area 310. The coupling mechanism used to keep payload 300 in the first orientation as door portion 108 rotates may now be designed to decouple and release payload 300 in the second orientation. One example of such decoupling is disclosed with reference to FIG. 3E.

FIG. 3D illustrates a side view of the deployment of the payload 300. In this regard, the door portion 108 and payload 300 (of FIG. 3B) are rotated within the body portion 102 so that it is partly obscured by the body portion 102. The position of the door portion 108 exposes an inner cavity or bay area 310 that houses the payload 300. Payload 300 may then be released. In some embodiments, the releasing force may be approximately equal to the gravitation force 305 acting on payload 300. In further embodiments, at least one force generating mechanism 208 may provide a contributing push against payload 300 to facilitate a more forceful release.

In addition to the release forces acting upon the payload 300 (e.g., gravitation force 305), a mechanism coupling the door portion 108 and the payload 300 enables a transition of the payload from the first orientation to the second orientation and, in turn, transfers an angular momentum to payload 300 as door portion 108 rotates within the body of the launcher to expose bay area 310. Said angular momentum provides for a “rolling release” of the payload as it exits bay area 310. FIG. 3E illustrates one example of such coupling mechanism.

In some embodiments, payload 300 may comprise, for example, a first contact pin 315 and a second contact pin 320. The contact pins 315, 320 may be detachably coupled, or inserted, into at least one bracket 202 or “notch”. As the door portion 108 rotates about rotational axis 303, the at least one bracket 202, by way of the contact pins 315. 320 (the specific pin may depend upon the rotational direction 301), transfers the angular momentum to payload 300 along the rotational direction 301. Accordingly, in this illustrated example, the contact pins 315, 320 and bracket (or notch) 202 serve as a pivot point for rolling release of the payload 300 out of bay area 310.

In the illustrated example embodiments in FIGS. 3A-3E, payload 300 is a drone that has retractable and extendable wings another flight surfaces. As bay area 310 is exposed by means of door portion 108's rotation, certain surfaces of payload 300 may begin to expand. Force generating means 208 (not illustrated in FIG. 3E) may provide an additional source of energy to increase the displacement of payload 300 as it continues to expand. Accordingly, where the payload may be designed to expand upon a release from the launcher, such expansion may occur a greater displacement from the launcher than would otherwise occur without the additional force provided by the force generating mechanism.

FIG. 4 illustrates another example embodiment of the launcher device 400. The device 400 as shown in FIG. 4 is operative to receive and launch a munition 405 in a similar way as discussed above in FIGS. 3A to 3D where the payload 300 was stored and launched. Some payload may have different coupling mechanisms, while some payloads may have no coupling mechanisms at all. As described above, launcher 100 may be adapted to carry and launch any type of payload that will fit in the cavity 304 of the launcher 100.

FIG. 5 illustrates a front view of a distal end portion of the door portion 108. The axis of rotation of the door portion 108 is shown by the element 501, for receiving a control element from control portion 204. FIG. 5 shows a locking mechanism 500 as shown in the illustrated example embodiment that a includes a pin 502 that is operative to engage and disengage a rotation capability of door portion 108. A control mechanism 504 may be operative with control portion 204 to engage or disengage pin 502. Accordingly, the travel of the door portion 108 is substantially impeded when the locking mechanism 500. The engagement of the pin substantially retains the door portion 108 and prevents the door from rotating about the element 501 undesirably.

Embodiments of the present disclosure provide a hardware and software platform operative by a set of methods and computer-readable media comprising instructions configured to operate the aforementioned modules and computing elements in accordance with the methods. The following depicts an example of at least one method of a plurality of methods that may be performed by at least one of the aforementioned modules. Various hardware components may be used at the various stages of operations disclosed with reference to each module.

For example, although methods may be described to be performed by a single computing device, it should be understood that, in some embodiments, different operations may be performed by different networked elements in operative communication with the computing device. For example, at least one computing device 700 may be employed in the performance of some or all of the stages disclosed with regard to the methods. Similarly, an apparatus may be employed in the performance of some or all of the stages of the methods. As such, the apparatus may comprise at least those architectural components as found in computing device 700.

Furthermore, although the stages of the following example method are disclosed in a particular order, it should be understood that the order is disclosed for illustrative purposes only. Stages may be combined, separated, reordered, and various intermediary stages may exist. Accordingly, it should be understood that the various stages, in various embodiments, may be performed in arrangements that differ from the ones claimed below. Moreover, various stages may be added or removed from the without altering or deterring from the fundamental scope of the depicted methods and systems disclosed herein.

FIG. 6 illustrates a block diagram of an example method 600 for operation of the launcher 100. In block 602, the launcher 100 powers up and determines whether door portion 108 is closed and the lock pin 502 is engaged. In block 604, the health of payload 300 and the navigation portions are checked for proper operation. A launch command is received in block 606.

In block 608, the lock pin 502 is disengaged, which allows door portion 108 to rotate. In block 610 lock pin 502 door portion 108 rotates open. In block 612, a signal indicating the door is opened is received. In block 614 an empty bay area 310 is detected. The locking pin 502 is re-engaged in block 616. The door portion 108 is then closed. In block 620 a signal indicating the door portion 108 is closed is received. In block 622 the launcher 100 powers off.

In some embodiments, the payload may be launched using a spring or biasing arrangement that may induce a substantially downward force on the payload during launch.

FIG. 8A illustrates an embodiment of the payload deployment mechanism 1105 illustrating the deployment of a detachably connected payload (e.g., the configurable payload 300). In the illustrated example of FIG. 8A, the payload 300 is deployed at least in part using the force generating mechanism 208. The payload deployment mechanism 1105 may also utilize a payload drag mechanism 810 to separate the configurable payload 300 from the payload deployment mechanism 1105. In some embodiments of the present disclosure, the payload 300 may be configured with a parachute 820. The payload deployment mechanism 1105 may include a door portion 108 that is detachably connected to payload deployment mechanism 1105. In some embodiments, the door portion 108 may be detachable from the payload 300. In other embodiments, the door portion 108 may be integrated into the construction of payload 300. In still other non-limiting embodiments, the door portion 108 may be an independent mechanism. The door portion 108 may not be attached to payload 300. Additionally, the door portion 108 may be configured to incorporate the payload drag mechanism 810 into the door portion 108. In some embodiments, the door portion 108 may enclose at least a portion of the payload deployment mechanism 1105.

In the attached state, the door portion 108 may be attached to the payload deployment mechanism 1105. The door portion 108 may be disposed flush with an outer surface of the payload deployment mechanism 1105 when the payload is in the attached state. The door portion 108 may be configured such that the door portion has minimal effect on the aerodynamics of the payload deployment mechanism 1105. In further embodiments the door portion 108 may be configured to detach from the payload deployment mechanism 1105. Door portion 108 may be attached to payload 300. The door portion 108 may be configured to detach from the payload deployment mechanism 1105 such that the detachment of the door portion 108 is associated with the deployment of the payload 300. Accordingly, in some embodiments the door portion 108 may be connected to the payload deployment mechanism 1105 such that it may secure the payload 300 within the payload deployment mechanism 1105.

The payload 300 may be attached to a bay area 310 of the payload deployment mechanism 1105. In some embodiments, at least one bracket 202 may detachably couple the payload 300 to the payload deployment mechanism 1105. The payload 300 may be coupled to bay area 310 of the payload deployment mechanism 1105. In some embodiments the at least one bracket 202 may be configured to attach the payload 300 to the door portion 108 of payload deployment mechanism 1105. Detachably coupling the payload 300 to the payload deployment mechanism 1105 may maintain the payload's position and orientation within the payload deployment mechanism 1105. For example, the at least one bracket 202 may be detachably coupled to the payload using a releasable or detachable coupling mechanism to secure the payload within the payload deployment mechanism 1105. For example, the at least one bracket 202 may be used as a coupling mechanism, as disclosed with reference to FIG. 3E.

In some embodiments, the payload drag mechanism 810 may be positioned at the forward portion of the payload 300. As illustrated in a non limiting embodiment in FIG. 8A the payload drag mechanism 810 may be positioned at the forward portion of the payload 300. In some embodiments, the payload drag mechanism 810 is flush with the payload deployment mechanism 1105 while the payload 300 is in the attached state with the payload deployment mechanism. The payload 300 may be integrated with the payload drag mechanism 810. The door portion 108 may be attached to the payload drag mechanism 810. In a non-limiting example in accordance with the present disclosure, the payload drag mechanism 810 may be attached to the payload 300 before the payload is connected to the payload deployment mechanism 1105.

The payload deployment mechanism 1105 may be integrated into the construction of the payload 300. The payload 300 may be pre-configured for the payload deployment mechanism 1105. The payload 300 may be pre-connected to the payload deployment mechanism 1105. In accordance with some embodiments of the present disclosure, the payload 300 may be constructed to integrate at least one of: the door portion 108, the payload drag mechanism 810, the force generating mechanism 208, and/or the parachute 820. Additional embodiments according to the present disclosure may include a configuration of the payload drag mechanism 810 that may be integrated with the door portion 108. The payload drag mechanism 810 may be an airfoil or other mechanism that may be configured to generate a force (e.g., drag) that may assist in the separation of the configurable payload 300 from the payload deployment mechanism 1105.

In some embodiments, the payload 300 may separate from the payload deployment mechanism 1105 at least partially in response to forces applied to the payload by the force generating mechanism 208. The door portion 108 may begin to separate from the payload deployment mechanism 1105 in response to at least one force from the force generating mechanism 208. For example, the force generating mechanism 208 may apply a force to the configurable payload 300 that may also separate the door portion 108 from the payload deployment mechanism 1105. As another example, the force generating mechanism 208 may directly apply at least one force to the door portion 108 that may cause initial separation of the door portion from payload deployment mechanism 1105.

As the payload 300 begins to separate from the payload deployment mechanism 1105, at least the payload drag mechanism 810 may be at least partially exposed. Once the payload drag mechanism 810 separates from the payload deployment mechanism 1105, the payload drag mechanism 810 may generate additional force (e.g., drag) applied to the payload 300. One embodiment of the present disclosure may generate a force in response to exposure of the payload 300 to the environment external to the payload deployment mechanism 1105. The additional force may aid in separating the payload 300 from the payload deployment mechanism 1105 as illustrated in one embodiment in FIG. 8A. In accordance with some embodiments of the present disclosure, the door portion 108 may be attached to payload 300. In such embodiments the forces generated by the payload drag mechanism 810 may be applied to both the door portion 108 and the payload 300. The additional forces may result from the attachment between the door portion 108 and the payload 300. The door portion 108 may separate from the payload deployment mechanism 1105 independently of the payload 300. Where the door portion 108 separates from the payload deployment mechanism 1105 independently of the payload 300, the door portion 108 may still apply a force to the payload 300 that may assist in deployment of the payload 300 from the payload deployment mechanism 1105.

In some embodiments, the deployment of the payload 300 may cause the deployment of a parachute 820. In some embodiments of the payload deployment mechanism 1105, the parachute 820 may be attached to the payload 300. In other embodiments, the parachute 820 may be attached to the payload drag mechanism 810. The parachute 820 may be stored within the payload deployment mechanism 1105 prior to separation of the payload 300.

The parachute 820 may be configured to deploy with the configurable payload 300. For example, the parachute 820 may be attached to the payload. For example, the parachute 820 may be directly attached to the payload. Embodiments may include the parachute 820 being a static line parachute. Embodiments of the present disclosure may also include the parachute 820 attached to the payload drag mechanism 810 which is in turn attached to the payload. In some embodiments of the present disclosure, deployment of the payload 300 may also cause deployment of the parachute 820. As the configurable payload 300 separates from the payload deployment mechanism 1105, the parachute 820 may also be deployed. In some embodiments the parachute 820 may be stored within the payload deployment mechanism 1105 until deployment. In other embodiments, the parachute 820 may be integrated into the construction of the configurable payload 300. In some embodiments, the parachute 820 may be configured to deploy in response to deployment of the payload 300. As shown in FIG. 8B, after deployment, the parachute 820 may be configured to open fully to provide deceleration for the payload 300 attached thereto.

In some embodiments, parachute deployment characteristics may be configured depending on, for example, requirements of the configurable payload 300. Parachute deployment characteristics may also utilize characteristics associated with the payload deployment. For example, the amount of time between separation of payload 300 from payload deployment mechanism 1105 and the deployment of parachute 820 can be controlled based on requirements of the configurable payload 300. In some embodiments, other characteristics may be used to determine parachute deployment such as at least one of: the velocity of the configurable payload 300, altitude of the configurable payload, or amount of separation between the configurable payload 300 and the payload deployment mechanism 1105.

FIG. 9 is a flow chart setting forth the general stages involved in a method 900 consistent with embodiments of the disclosure for deployment of the payload. Method 900 may be implemented using a computing device 700 or any other component associated with the launcher 100. For illustrative purposes alone, computing device 700 is described as one potential actor in the following stages. In embodiments, an apparatus (e.g., the launcher 100) may be configured to receive the configurable payload in stage 905. For example, the launcher may be configured with a detachable means for connecting the payload to the apparatus. As a particular example, the detachable means for connecting the payload to the apparatus may include one or more of fasteners, clips, electromechanical connections, or other passive or controllable means for detachably connecting the payload to the apparatus. Detachably connecting the payload to the apparatus may ensure that the payload can be secured within the apparatus until deployment. In some embodiments, the detachable connecting means may allow for decoupling of the payload from the apparatus without application of force. In other embodiments it may be necessary to apply a decoupling force to disengage the detachable means for coupling, decoupling the apparatus from the payload. The application of the decoupling force may result in a greater separation rate of the payload from the apparatus that may decrease the overall deployment time.

In stage 910 the payload may be detachably connected to the apparatus. For example, the payload may be detachably connected to the apparatus within a cargo bay area of the apparatus. According to some embodiments, the payload may be substantially housed within the bay area. In some embodiments, the payload may remain partly exposed to the external environment when connected to the apparatus. The partially exposed payload may be configured to improve the aerodynamic efficiency of the apparatus when connected to the apparatus. In other embodiments, the payload may be substantially housed within the apparatus. The apparatus may be designed or configured to achieve maximum performance, such as minimum aerodynamic drag, if the payload may be connected to the apparatus.

The apparatus may receive the payload through engagement of the detachable means for connecting the payload apparatus as described in stage 905, such that the apparatus and the payload may be mechanically connected. Alternatively or additionally, the payload may be electrically and/or communicatively connected to the apparatus. The payload electrical and/or communicative connection to the apparatus may utilize additional means of connection instead of or in addition to the mechanical connection to the apparatus. Such connection between the payload and the apparatus may enable coordination between the apparatus and the payload during deployment.

In stage 915, the apparatus may receive an indication to deploy the payload. The indication may correspond to deployment initiation of the payload from the apparatus. The apparatus may receive the indication in many different forms that enable the apparatus to determine the initiation of payload deployment. For example, the indication may be an electrical signal, a digital communication, or a physical indication for deployment.

Once the indication has been received to deploy the payload, the apparatus proceeds to stage 920, in which the payload detaches from the apparatus. That is, responsive to the indication to deploy the payload, the detachable connection between the payload and the apparatus may disengage. In some embodiments the connection may be single-use and the payload may break away from the apparatus. In other embodiments, the apparatus may cause the detachable connection to disengage, decoupling the payload from the launcher. The detachment of the payload from the apparatus allows for physical separation of the payload from the apparatus.

To aid in separation of the payload from the apparatus, a force may be applied to the payload in stage 925. The force applied to the payload may be from a mechanism associated with the apparatus. For example, the force may be applied by a force generating mechanism or other mechanism that enables the separation of the payload from the apparatus. In other embodiments the force applied to the payload may be applied from a source external to the apparatus. The external force applied to the payload may come from air resistance, drag, gravity, or a change in momentum of the apparatus once the payload is detached from the apparatus. For example, the force may be applied by a payload drag mechanism.

In stage 930, the payload may be fully deployed. In some embodiments, the payload may be considered to be fully deployed when the payload reaches a threshold separation distance from the apparatus.

Once the payload has been deployed, a velocity altering and/or guiding device may optionally be used to control the velocity and/or direction of the payload. For example, a parachute may be used to slow descent of the payload following deployment. As another example, one or more airfoils and/or ailerons may be deployed to control velocity and/or direction of the payload following deployment.

FIG. 10 is a flow chart setting forth the general stages involved in a method 1000 consistent with embodiments of the disclosure for deployment of the payload. Accordingly, Method 1000 demonstrates an additional non-limiting example of the function of the present disclosure. Method 1000 may be implemented using a computing device 700 or any other component associated with the launcher 100. For illustrative purposes alone, computing device 700 is described as one potential actor in the following stages. In embodiments, an apparatus (e.g., the launcher 100) may be configured with a detachable means to receive the configurable payload in stage 1005 that may include one or more of fasteners, clips, electromechanical connections, or other passive or controllable means for detachably connecting the payload to the apparatus in stage 1005. In some embodiments, the detachable connecting means may allow for decoupling of the payload from the apparatus without application of force. In other embodiments it may be necessary to apply a decoupling force to disengage the detachable means for coupling, decoupling the apparatus from the payload. The application of the decoupling force may result in a greater separation rate of the payload from the apparatus that may decrease the overall deployment time.

In stage 1010 the launcher may receive the detachably connected payload within the bay area of the apparatus. For example, the payload may be detachably connected to the apparatus within a cargo bay area of the apparatus. According to some embodiments, the payload may be substantially housed within the bay area. In some embodiments, the payload may remain partly exposed to the external environment when connected to the apparatus. The partially exposed payload may be configured to improve the aerodynamic efficiency of the apparatus when connected to the apparatus. In other embodiments, the payload may be substantially housed within the apparatus. The apparatus may be designed or configured to achieve maximum performance, such as minimum aerodynamic drag, if the payload may be connected to the apparatus.

The apparatus may receive the payload through engagement of the detachable means for connecting the payload apparatus as described in stage 1005, such that the apparatus and the payload may be mechanically connected. Alternatively or additionally, the detachable means for connecting the payload may also be electrically and/or communicatively connected to the apparatus through a wired or wireless communication device. The payload electrical and/or communicative connection to the apparatus may utilize additional means of connection instead of or in addition to the mechanical connection to the apparatus. Such connection between the payload and the apparatus may enable coordination between the apparatus and the payload during deployment.

In stage 1015, the apparatus may receive a means for indicating the deployment of the payload. The indication may correspond to deployment initiation of the payload from the apparatus. The apparatus may receive the means of indicating in many different forms that enable the apparatus to determine the initiation of payload deployment. For example, the means for indicating may be an electrical signal, a digital communication, or a physical indication for deployment.

Once the indication has been received to deploy the payload, the apparatus proceeds to stage 1020, in which the payload detaches from the apparatus. That is, responsive to the indication to deploy the payload, the detachable connection between the payload and the apparatus may disengage. In some embodiments the connection may be single-use and the payload may break away from the apparatus. In other embodiments, the apparatus may cause the detachable connection to disengage, decoupling the payload from the launcher. The detachment of the payload from the apparatus allows for physical separation of the payload from the apparatus.

To aid in separation of the payload from the apparatus, a force may be applied to the payload in stage 1025. The force applied to the payload may be from a force generating means associated with the apparatus. For example, the force generating means may be applied by a force generating mechanism or other mechanism that enables the separation of the payload from the apparatus. In other embodiments the force applied to the payload may be applied from a source external to the apparatus. The external force applied to the payload may come from air resistance, drag, gravity, or a change in momentum of the apparatus once the payload is detached from the apparatus. For example, the force may be applied by a payload drag mechanism.

In stage 1030, the payload may be fully deployed. In some embodiments, the payload may be considered to be fully deployed when the payload reaches a threshold separation distance from the apparatus.

Once the payload has been deployed, a velocity altering and/or guiding device may optionally be used to control the velocity and/or direction of the payload. For example, a parachute may be used to slow descent of the payload following deployment. As another example, one or more airfoils and/or ailerons may be deployed to control velocity and/or direction of the payload following deployment.

The embodiments described above offer a launcher device that is operative to receive and retain a drone or other payload in a protected launcher. The launcher helps to reduce the drag of the payload and to protect the payload from environmental factors. The payload is launched when a rotating door opens to expose the payload. The rotating door may be parallel or concentric to a longitudinal axis of the body portion 102 of the device.

FIGS. 11A-14C illustrate the utilization of an example hinge mechanism during the separation of a payload. Accordingly, in some embodiments, the payload deployment mechanism 1105 may comprise a hinge mechanism 1110. The hinge mechanism 1110 may enable the configurable payload 300 to separate from the payload deployment mechanism 1105 without contacting the payload deployment mechanism 1105. In some embodiments, the hinge mechanism 1110 may be located at the aft end of the configurable payload 300. The hinge mechanism 1110 may be located in a position to enable positioning of the payload 300 within the bay area 310 of the payload deployment mechanism 1105. The location may enable a controlled separation of the configurable payload 300 from the payload deployment mechanism 1105 during operation of the System, such that the payload 300 does not contact the payload deployment mechanism 1105 during the deployment or after the deployment.

In some embodiments, the hinge mechanism 1110 may control the separation of the configurable payload 300 from the payload deployment mechanism 1105. The hinge mechanism 1110 may enable the configurable payload 300 to pivot about a pivot point located external to the payload deployment mechanism 1105. The pivot point of the hinge mechanism 1110 may ensure the pivoting motion of the payload 300 does not intersect with the payload deployment mechanism 1105. Further still, the hinge mechanism 1110 may be designed to be located within the payload deployment mechanism 1105 while maintaining the pivot point external to the payload deployment mechanism, which helps to prevent the configurable payload 300 from contacting the payload deployment mechanism 1105 during the deployment of the configurable payload 300. In various embodiments, the hinge mechanism 1110 may help to guide the release of the configurable payload 300 away from the payload deployment mechanism 1105 such that the configurable payload 300 does not contact the payload deployment mechanism 1105 during (or subsequent to) release.

In some embodiments, the payload deployment mechanism 1105 may comprise a force generating mechanism 208 that may help to initiate separation of the configurable payload 300 from the payload deployment mechanism. The force generating mechanism 208 may be configured to apply a force to the configurable payload 300 that may urge the payload along the path determined at least in part by the hinge mechanism 1110. In some embodiments, the force generating mechanism 208 may be configured within the hinge mechanism 1110. Alternatively or additionally, the force generating mechanism 208 may be integrated into the hinge mechanism 1110. Still further, the force applying mechanism may be disposed within the payload deployment mechanism 1105 and external to the hinge mechanism 1110. The force generating mechanism 208 may comprise at least one of: a spring, a position, a propellant, or any other force generating mechanism to assist in deploying the configurable payload 300.

In embodiments of the present disclosure, the hinge mechanism 1110 may include one or more hinge components that can be used to help guide the configurable payload 300 along a release path. In some embodiments, the hinge mechanism 1110 may comprise a plurality of hinge components, at least one of which may be located on the payload deployment mechanism 1105. In some embodiments, at least one of the plurality of hinge components may be attached to the configurable payload 300. The hinge components may work together, for example functioning as a mating pair, hinge, guided path, or other set of elements that would guide the release of the configurable payload 300. For example, as shown in FIGS. 11A-11C, the hinge mechanism 1110 may comprise hinge components including a first hinge component 1116 attached to the of payload deployment mechanism 1105 and a second hinge component 1117 attached to the configurable payload 300. As one particular example, the hinge mechanism 1110 may comprise a partial cylindrical hinge. The partial cylindrical hinge may comprise a plurality of hinge components (e.g., at least the first hinge component 1116 and the second hinge component 1117) configured to rotate about a fixed pivot point. The pivot point of the hinge mechanism 1110 may be external to the payload deployment mechanism 1105. Accordingly, the hinge components of the partial cylindrical hinge may be configured to translate along the radius of the pivot arc. This demonstrates one way in which the hinge mechanism 1110 may guide the configurable payload 300 along a release path such that the release path of the configurable payload does not contact the payload deployment mechanism 1105 during or subsequent to deployment. The hinge mechanism 1110 may further comprise components including a cylindrical hinge and a mating cavity to assemble the hinge mechanism 1110.

In various embodiments, the hinge mechanism 1110 may comprise at least a first hinge component 1116 and a second hinge component 1117. The first hinge component 1116 and the second hinge component 1117 may comprise associated hinge components. For example, the first hinge component 1116 may be formed as a protrusion from the configurable payload 300, configured to detachably connect to and/or mate with the second hinge component 1117. The second hinge component 1117 may define a recess within the payload deployment mechanism 1105. The second hinge component 1117 may be configured to guide the first hinge component 1116 along a specific path. The path determined by the hinge mechanism 1110 may prevent the configurable payload 300 attached to the first hinge component 1116 from contacting the payload deployment mechanism 1105 during deployment. The first hinge component 1116 and the second hinge component 1117 may be located on independent portions of the payload deployment mechanism 1105 and/or the configurable payload 300. For example, the hinge mechanism 1110 may utilize a first hinge component 1116 located on the payload deployment mechanism 1105 and the second hinge component 1117 located on the configurable payload 300. A first hinge component located on the configurable payload and a second hinge component located on the payload deployment mechanism, first and second hinge components located on the payload deployment mechanism, or first and second hinge components located on the payload. The locations of each of the first hinge component 1116 and the second hinge component 1117 may be determined at least in part by the requirements of the configurable payload. The location of the hinge mechanism 1110 and/or the locations of each of the first hinge component 1116 and the second hinge component 1117 may additionally or alternatively be determined by at least one other factor, such as payload mechanism requirements, the configuration of the payload deployment mechanism 1105 or other mechanical or aerodynamic considerations.

As a non-limiting example, the first hinge component 1116 may be a protrusion that may correspond to the release path of the configurable payload 300. The second hinge component 1117 may include a cavity configured to releasably retain the first hinge component. The second hinge component 1117 may be configured to guide the first hinge component 1116 along the release path of the configurable payload. The first hinge component 1116 may be configured to translate along the of the pivot arc (e.g., the release path defined by the second hinge component 1117) and rotate the configurable payload about a pivot point external to the payload deployment mechanism 1105.

The first hinge component 1116 and the second hinge component 1117 may be constructed to support the forces associated with the separation of the configurable payload 300 from the payload deployment mechanism 1105. In some embodiments, the first hinge component 1116 and the second hinge component 1117 may support forces on the hinge mechanism 1110 that may result from drag generated from the separation of the configurable payload 300 from the payload deployment mechanism 1105. The hinge mechanism 1110 may be constructed such that the hinge components (e.g., the first hinge component 1116 and the second hinge component 1117) may separate after the first hinge component 1116 and the second hinge component 1117 rotate beyond a predefined threshold. The rotation between the first hinge component 1116 and the second hinge component 1117 may be associated with deploying the configurable payload 300. The separation of the first hinge component 1116 and the second hinge component 1117 may be associated with the separation of the configurable payload 300 from the payload deployment mechanism 1105. The hinge mechanism 1110 may be disposed within the bay area 310 of the payload deployment mechanism 1105. The hinge mechanism 1110 may releasably attach the configurable payload 300 to the payload deployment mechanism 1105. In some embodiments, the hinge mechanism 1110 may be attached to other portions of the payload deployment mechanism 1105. The hinge mechanism 1110 may be configured to guide the release of the configurable payload 300. The hinge mechanism 1110 may be configured to guide the configurable payload 300 along a path to avoid contacting the payload deployment mechanism 1105 or any other platform to which the payload deployment mechanism would relate.

The payload deployment mechanism 1105 may comprise a latch assembly comprising at least one bracket 202 that supports the retention of the configurable payload 300 within payload deployment mechanism 1105. In some embodiments, the latch assembly may comprise one or more of the biasing and/or fastening mechanisms. In some embodiments of the present disclosure, the at least one bracket 202 may attach to the configurable payload 300 using the payload drag mechanism 810. The payload drag mechanism 810 may be located on the forward edge of the configurable payload 300 and/or at least one of the side portions of the payload.

In some embodiments, the payload deployment mechanism 1105 may comprise a vent 1350 configured to direct external airflow into the payload deployment mechanism 1105 as shown in FIGS. 13A-C and 14A-C. FIG. 13A illustrates an embodiment of the configurable payload 300 within the payload deployment mechanism 1105. The first hinge component 1116 and the second hinge component 1117, may be configured such that they may secure the payload 300 within the payload deployment mechanism. The first hinge component 1116 and the second hinge component 1117 may be configured to enable unrestricted movement along the deployment path of the configurable payload 300. In some embodiments the hinge mechanism 1110 may be configured to enable unrestricted release for the configurable payload 300, while the configurable payload 300 is stored within the payload deployment mechanism 1105.

FIG. 12B illustrates an embodiment of the hinge mechanism 1110 displaced partially along the path of release of the configurable payload 300. The first hinge component 1116 and the second hinge component 1117 may guide the configurable payload 300 during deployment of the payload from the payload deployment mechanism 1105. FIG. 12C illustrates an embodiment of the hinge mechanism 1110 displaced prior to detachment of the hinge mechanism 1110 from the payload deployment mechanism 1105 along the path of release of the configurable payload 300. As shown in FIGS. 13A-13C, the vent 1350 may enable the payload deployment mechanism 1105 to maintain pressure equilibrium between the external environment and the payload deployment mechanism 1105 during the deployment of the configurable payload 300. In embodiments, the vent 1350 may comprise a path for airflow between the external environment and the payload deployment mechanism. The vent 1350 may be integrated into the external profile of the payload deployment mechanism 1105. The vent 1350 may be constructed to minimize drag generated by the vent 1350 prior to separation of the configurable payload 300 from the payload deployment mechanism 1105. In some embodiments, the vent 1350 may be configured to equalize pressure between the external environment and the payload deployment mechanism 1105 at a rate equivalent to the displacement rate of the configurable payload 300 during separation from the payload deployment mechanism 1105. For example, the vent 1350 may help to reduce or eliminate the pressure differential retaining the configurable payload 300 in a retained position in response to initiation of the deployment of the configurable payload 300. After separation of the configurable payload 300 from the payload deployment mechanism 1105, the vent 1350 may allow for airflow to continue without disrupting operation of the payload deployment mechanism 1105. The vent 1350 may be configured to minimize drag after the configurable payload 300 has separated from the payload deployment mechanism 1105.

In some embodiments, the vent 1350 may redirect airflow from the external environment to provide an additional force that may assist in the separation of the payload 300. Embodiments of the payload deployment mechanism may enable the vent 1350 to provide an additional force to assist in the separation of the payload 300 from the payload deployment mechanism 1105. FIG. 13A illustrates a non-limiting embodiment of the present disclosure of the configurable payload 300 secured within the payload deployment mechanism 1105. The payload drag mechanism 810 may be constructed to be substantially flush with the payload deployment mechanism 1105 while the payload is in the retained position, as shown in FIG. 13A. For example, the payload drag mechanism 810, may secure the configurable payload 300 to the payload deployment mechanism 1105 using at least one bracket. The aft portion of payload 300 may be secured to the payload deployment mechanism using the hinge mechanism 1110. The hinge mechanism may be utilized to help secure the payload 300 to the payload deployment mechanism 1105. The payload deployment mechanism 1105 may be configured with a vent 1350. The vent 1350 may be configured to minimally affect aerodynamics of the payload deployment mechanism 1105.

FIG. 13B illustrates a non-limiting embodiment of the present disclosure of the payload 300 partially separated from the payload deployment mechanism 1105. In a non-limiting example, the payload 300 may initially separate from the payload deployment mechanism at the location of the payload drag mechanism 810. The hinge mechanism 1110 may guide the payload 300 along the deployment path. The deployment path of payload 300 may be at least partially controlled by the interaction between the first hinge component 1116 and the second hinge component 1117 of the hinge mechanism 1110. In some embodiments of the present disclosure, release, separation or uncoupling of the at least one bracket 202 may be associated with initiation of the separation of the payload 300 from the payload deployment mechanism 1105. The at least one bracket 202 may separate such the payload 300 may begin to separate from the payload deployment mechanism 1105. In some embodiments, the bracket may release the payload 300 to initiate separation of the payload 300 from the payload deployment mechanism 1105. The vent 1350 may allow airflow from the external environment into the payload deployment mechanism 1105. The vent 1350 may be configured to provide enough airflow to the payload deployment mechanism 1105 to enable the payload 300 to separate from the payload deployment mechanism. In particular, the vent 1350 may equalize the pressure within the payload deployment mechanism 1105 to the ambient pressure surrounding the payload deployment mechanism 1105, thereby allowing the payload to separate from the payload deployment mechanism.

FIG. 13C illustrates a non-limiting embodiment of the present disclosure prior to the separation of the payload 300 from the payload deployment mechanism 1105. The hinge mechanism 1110 may be configured with a pivot point external from the payload deployment mechanism 1105. The first hinge component 1116 and the second hinge component 1117 may be configured to guide payload 300 along a deployment path such that payload 300 does not contact the payload deployment mechanism 1105.

FIG. 14A illustrates a non-limiting embodiment of a perspective view of the payload deployment mechanism 1105. In some embodiments of the present disclosure, the payload 300 may be configured to be attached to at least one of the first hinge component 1116 and the second hinge component 1117. The first hinge component 1116 may attach to payload 300. The second hinge component 1117 may attach to payload deployment mechanism 1105. FIG. 14B illustrates perspective view of a non-limiting embodiment of the payload 300 partially separated from the payload deployment. The vent 1350 may be configured to connect to the internal portion of the payload deployment mechanism 1105 to the external environment. The vent 1350 may be configured to reach the location where payload 300 may be secured within the payload deployment mechanism 1105. In this way, the vent 1350 may allow for equalization of pressure between the payload deployment mechanism 1105 and the external environment, reducing forces that would otherwise retain the payload within the payload deployment mechanism. FIG. 14C illustrates a perspective view of a non-limiting embodiment of the payload deployment mechanism 1105 prior to the separation of payload 300 from the payload deployment mechanism. The payload 300 may be attached to the hinge mechanism 1110.

In some embodiments, the payload deployment mechanism 1105 may be controlled by the launcher 100. The launcher 100 may configure the payload deployment mechanism 1105. The launcher 100 may configure the payload deployment mechanism 1105 to control the deployment of the payload 300. The payload deployment mechanism 1105 may be controlled directly by a computing device 700.

Launcher 100 may comprise the components of a computing device 700 as illustrated in FIG. 7 . Additionally or alternatively, the launcher 100 may operable by and/or in conjunction with the computing device 700, which may comprise, but not be limited to the following:

Mobile computing device, such as, but is not limited to, a laptop, a tablet, a smartphone, a drone, a wearable, an embedded device, a handheld device, an Arduino, an industrial device, or a remotely operable recording device;

A supercomputer, an exa-scale supercomputer, a mainframe, or a quantum computer;

A minicomputer, wherein the minicomputer computing device comprises, but is not limited to, an IBM AS400/iSeries/System I, A DEC VAX/PDP, a HP3000, a Honeywell-Bull DPS, a Texas Instruments TI-990, or a Wang Laboratories VS Series;

A microcomputer, wherein the microcomputer computing device comprises, but is not limited to, a server, wherein a server may be rack mounted, a workstation, an industrial device, a raspberry pi, a desktop, or an embedded device;

FIG. 7 is a block diagram of a system including computing device 700. Consistent with an embodiment of the disclosure, the aforementioned CPU 720, the bus 730, the memory unit 740, a PSU 750, and the plurality of I/O units 760 may be implemented in a computing device, such as computing device 700 of FIG. 7 . Any suitable combination of hardware, software, or firmware may be used to implement the aforementioned units. For example, the CPU 720, the bus 730, and the memory unit 740 may be implemented with computing device 700 or any of other computing devices 700, in combination with computing device 700. The aforementioned system, device, and components are examples and other systems, devices, and components may comprise the aforementioned CPU 720, the bus 730, the memory unit 740, consistent with embodiments of the disclosure.

A computing device 700 does not need to be electronic, nor even have a CPU 720, nor bus 730, nor memory unit 740. The definition of the computing device 700 to a person having ordinary skill in the art is “A device that computes, especially a programmable [usually] electronic machine that performs high-speed mathematical or logical operations or that assembles, stores, correlates, or otherwise processes information.” Any device which processes information qualifies as a computing device 700, especially if the processing is purposeful.

With reference to FIG. 7 , a system consistent with an embodiment of the disclosure may include a computing device, such as computing device 700. In a basic configuration, computing device 700 may include at least one clock module 710, at least one CPU 720, at least one bus 730, and at least one memory unit 740, at least one PSU 750, and at least one I/O 760 module, wherein I/O module may be comprised of, but not limited to a non-volatile storage sub-module 761, a communication sub-module 762, a sensors sub-module 763, and a peripherals sub-module 764.

A system consistent with an embodiment of the disclosure the computing device 700 may include the clock module 710 may be known to a person having ordinary skill in the art as a clock generator, which produces clock signals. Clock signal is a particular type of signal that oscillates between a high and a low state and is used like a metronome to coordinate actions of digital circuits. Most integrated circuits (ICs) of sufficient complexity use a clock signal in order to synchronize different parts of the circuit, cycling at a rate slower than the worst-case internal propagation delays. The preeminent example of the aforementioned integrated circuit is the CPU 720, the central component of modern computers, which relies on a clock. The only exceptions are asynchronous circuits such as asynchronous CPUs. The clock 710 can comprise a plurality of embodiments, such as, but not limited to, single-phase clock which transmits all clock signals on effectively 1 wire, two-phase clock which distributes clock signals on two wires, each with non-overlapping pulses, and four-phase clock which distributes clock signals on 4 wires.

Many computing devices 700 use a “clock multiplier” which multiplies a lower frequency external clock to the appropriate clock rate of the CPU 720. This allows the CPU 720 to operate at a much higher frequency than the rest of the computer, which affords performance gains in situations where the CPU 720 does not need to wait on an external factor (like memory 740 or input/output 760). Some embodiments of the clock 710 may include dynamic frequency change, where, the time between clock edges can vary widely from one edge to the next and back again.

A system consistent with an embodiment of the disclosure the computing device 700 may include the CPU unit 720 comprising at least one CPU Core 721. A plurality of CPU cores 721 may comprise identical CPU cores 721, such as, but not limited to, homogeneous multi-core systems. It is also possible for the plurality of CPU cores 721 to comprise different CPU cores 721, such as, but not limited to, heterogeneous multi-core systems, big.LITTLE systems and some AMD accelerated processing units (APU). The CPU unit 720 reads and executes program instructions which may be used across many application domains, for example, but not limited to, general purpose computing, embedded computing, network computing, digital signal processing (DSP), and graphics processing (GPU). The CPU unit 720 may run multiple instructions on separate CPU cores 721 at the same time. The CPU unit 720 may be integrated into at least one of a single integrated circuit die and multiple dies in a single chip package. The single integrated circuit die and multiple dies in a single chip package may contain a plurality of other aspects of the computing device 700, for example, but not limited to, the clock 710, the CPU 720, the bus 730, the memory 740, and I/O 760.

The CPU unit 720 may contain cache 722 such as, but not limited to, a level 1 cache, level 2 cache, level 3 cache or combination thereof. The aforementioned cache 722 may or may not be shared amongst a plurality of CPU cores 721. The cache 722 sharing comprises at least one of message passing and inter-core communication methods may be used for the at least one CPU Core 721 to communicate with the cache 722. The inter-core communication methods may comprise, but not limited to, bus, ring, two-dimensional mesh, and crossbar. The aforementioned CPU unit 720 may employ symmetric multiprocessing (SMP) design.

The plurality of the aforementioned CPU cores 721 may comprise soft microprocessor cores on a single field programmable gate array (FPGA), such as semiconductor intellectual property cores (IP Core). The plurality of CPU cores 721 architecture may be based on at least one of, but not limited to, Complex instruction set computing (CISC), Zero instruction set computing (ZISC), and Reduced instruction set computing (RISC). At least one of the performance-enhancing methods may be employed by the plurality of the CPU cores 721, for example, but not limited to Instruction-level parallelism (ILP) such as, but not limited to, superscalar pipelining, and Thread-level parallelism (TLP).

Consistent with the embodiments of the present disclosure, the aforementioned computing device 700 may employ a communication system that transfers data between components inside the aforementioned computing device 700, and/or the plurality of computing devices 700. The aforementioned communication system will be known to a person having ordinary skill in the art as a bus 730. The bus 730 may embody internal and/or external plurality of hardware and software components, for example, but not limited to a wire, optical fiber, communication protocols, and any physical arrangement that provides the same logical function as a parallel electrical bus. The bus 730 may comprise at least one of, but not limited to a parallel bus, wherein the parallel bus carry data words in parallel on multiple wires, and a serial bus, wherein the serial bus carry data in bit-serial form. The bus 730 may embody a plurality of topologies, for example, but not limited to, a multidrop/electrical parallel topology, a daisy chain topology, and a connected by switched hubs, such as USB bus. The bus 730 may comprise a plurality of embodiments, for example, but not limited to:

-   -   Internal data bus (data bus) 731/Memory bus     -   Control bus 732     -   Address bus 733     -   System Management Bus (SMBus)     -   Front-Side-Bus (FSB)     -   External Bus Interface (EBI)     -   Local bus     -   Expansion bus     -   Lightning bus     -   Controller Area Network (CAN bus)     -   Camera Link     -   ExpressCard     -   Advanced Technology management Attachment (ATA), including         embodiments and derivatives such as, but not limited to,         Integrated Drive Electronics (IDE)/Enhanced IDE (EIDE), ATA         Packet Interface (ATAPI), Ultra-Direct Memory Access (UDMA),         Ultra ATA (UATA)/Parallel ATA (PATA)/Serial ATA (SATA),         CompactFlash (CF) interface, Consumer Electronics ATA         (CE-ATA)/Fiber Attached Technology Adapted (FATA), Advanced Host         Controller Interface (AHCI), SATA Express (SATAe)/External SATA         (eSATA), including the powered embodiment eSATAp/Mini-SATA         (mSATA), and Next Generation Form Factor (NGFF)/M.2.     -   Small Computer System Interface (SCSI)/Serial Attached SCSI         (SAS)     -   HyperTransport     -   InfiniBand     -   RapidIO     -   Mobile Industry Processor Interface (MIPI)     -   Coherent Processor Interface (CAPI)     -   Plug-n-play     -   1-Wire     -   Peripheral Component Interconnect (PCI), including embodiments         such as, but not limited to, Accelerated Graphics Port (AGP),         Peripheral Component Interconnect eXtended (PCI-X), Peripheral         Component Interconnect Express (PCI-e) (e.g., PCI Express Mini         Card, PCI Express M.2 [Mini PCIe v2], PCI Express External         Cabling [ePCIe], and PCI Express OcuLink [Optical Copper{Cu}         Link]), Express Card, AdvancedTCA, AMC, Universal IO,         Thunderbolt/Mini DisplayPort, Mobile PCIe (M-PCIe), U.2, and         Non-Volatile Memory Express (NVMe)/Non-Volatile Memory Host         Controller Interface Specification (NVMHCIS).     -   Industry Standard Architecture (ISA), including embodiments such         as, but not limited to Extended ISA (EISA),         PC/XT-bus/PC/AT-bus/PC/104 bus (e.g., PC/104-Plus,         PCI/104-Express, PCI/104, and PCI-104), and Low Pin Count (LPC).     -   Music Instrument Digital Interface (MIDI)     -   Universal Serial Bus (USB), including embodiments such as, but         not limited to, Media Transfer Protocol (MTP)/Mobile         High-Definition Link (MHL), Device Firmware Upgrade (DFU),         wireless USB, InterChip USB, IEEE 1394 Interface/Firewire,         Thunderbolt, and eXtensible Host Controller Interface (xHCI).

Consistent with the embodiments of the present disclosure, the aforementioned computing device 700 may employ hardware integrated circuits that store information for immediate use in the computing device 700, know to the person having ordinary skill in the art as primary storage or memory 740. The memory 740 operates at high speed, distinguishing it from the non-volatile storage sub-module 761, which may be referred to as secondary or tertiary storage, which provides slow-to-access information but offers higher capacities at lower cost. The contents contained in memory 740, may be transferred to secondary storage via techniques such as, but not limited to, virtual memory and swap. The memory 740 may be associated with addressable semiconductor memory, such as integrated circuits consisting of silicon-based transistors, used for example as primary storage but also other purposes in the computing device 700. The memory 740 may comprise a plurality of embodiments, such as, but not limited to volatile memory, non-volatile memory, and semi-volatile memory. It should be understood by a person having ordinary skill in the art that the ensuing are non-limiting examples of the aforementioned memory:

-   -   Volatile memory which requires power to maintain stored         information, for example, but not limited to, Dynamic         Random-Access Memory (DRAM) 741, Static Random-Access Memory         (SRAM) 742, CPU Cache memory 725, Advanced Random-Access Memory         (A-RAM), and other types of primary storage such as         Random-Access Memory (RAM).     -   Non-volatile memory which can retain stored information even         after power is removed, for example, but not limited to,         Read-Only Memory (ROM) 743, Programmable ROM (PROM) 744,         Erasable PROM (EPROM) 745, Electrically Erasable PROM (EEPROM)         746 (e.g., flash memory and Electrically Alterable PROM         [EAPROM]), Mask ROM (MROM), One Time Programable (OTP) ROM/Write         Once Read Many (WORM), Ferroelectric RAM (FeRAM), Parallel         Random-Access Machine (PRAM), Split-Transfer Torque RAM         (STT-RAM), Silicon Oxime Nitride Oxide Silicon (SONOS),         Resistive RAM (RRAM), Nano RAM (NRAM), 3D Xpoint, Domain-Wall         Memory (DWM), and millipede memory.     -   Semi-volatile memory which may have some limited non-volatile         duration after power is removed but loses data after said         duration has passed. Semi-volatile memory provides high         performance, durability, and other valuable characteristics         typically associated with volatile memory, while providing some         benefits of true non-volatile memory. The semi-volatile memory         may comprise volatile and non-volatile memory and/or volatile         memory with battery to provide power after power is removed. The         semi-volatile memory may comprise, but not limited to         spin-transfer torque RAM (STT-RAM).

Consistent with the embodiments of the present disclosure, the aforementioned computing device 700 may employ the communication system between an information processing system, such as the computing device 700, and the outside world, for example, but not limited to, human, environment, and another computing device 700. The aforementioned communication system will be known to a person having ordinary skill in the art as I/O 760. The I/O module 760 regulates a plurality of inputs and outputs with regard to the computing device 700, wherein the inputs are a plurality of signals and data received by the computing device 700, and the outputs are the plurality of signals and data sent from the computing device 700. The I/O module 760 interfaces a plurality of hardware, such as, but not limited to, non-volatile storage 761, communication devices 762, sensors 763, and peripherals 764. The plurality of hardware is used by the at least one of, but not limited to, human, environment, and another computing device 700 to communicate with the present computing device 700. The I/O module 760 may comprise a plurality of forms, for example, but not limited to channel I/O, port mapped I/O, asynchronous I/O, and Direct Memory Access (DMA).

Consistent with the embodiments of the present disclosure, the aforementioned computing device 700 may employ the non-volatile storage sub-module 761, which may be referred to by a person having ordinary skill in the art as one of secondary storage, external memory, tertiary storage, off-line storage, and auxiliary storage. The non-volatile storage sub-module 761 may not be accessed directly by the CPU 720 without using intermediate area in the memory 740. The non-volatile storage sub-module 761 does not lose data when power is removed and may be two orders of magnitude less costly than storage used in memory module, at the expense of speed and latency. The non-volatile storage sub-module 761 may comprise a plurality of forms, such as, but not limited to, Direct Attached Storage (DAS), Network Attached Storage (NAS), Storage Area Network (SAN), nearline storage, Massive Array of Idle Disks (MAID), Redundant Array of Independent Disks (RAID), device mirroring, off-line storage, and robotic storage. The non-volatile storage sub-module (761) may comprise a plurality of embodiments, such as, but not limited to:

-   -   Optical storage, for example, but not limited to, Compact         Disk (CD) (CD-ROM/CD-R/CD-RW), Digital Versatile Disk (DVD)         (DVD-ROM/DVD-R/DVD+R/DVD-RW/DVD+RW/DVD±RW/DVD+R         DL/DVD-RAM/HD-DVD), Blu-ray Disk (BD) (BD-ROM/BD-R/BD-RE/BD-R         DL/BD-RE DL), and Ultra-Density Optical (UDO).     -   Semiconductor storage, for example, but not limited to, flash         memory, such as, but not limited to, USB flash drive, Memory         card, Subscriber Identity Module (SIM) card, Secure Digital (SD)         card, Smart Card, CompactFlash (CF) card, Solid-State Drive         (SSD) and memristor.     -   Magnetic storage such as, but not limited to, Hard Disk Drive         (HDD), tape drive, carousel memory, and Card Random-Access         Memory (CRAM).     -   Phase-change memory     -   Holographic data storage such as Holographic Versatile Disk         (HVD).     -   Molecular Memory     -   Deoxyribonucleic Acid (DNA) digital data storage

Consistent with the embodiments of the present disclosure, the aforementioned computing device 700 may employ the communication sub-module 762 as a subset of the I/O 760, which may be referred to by a person having ordinary skill in the art as at least one of, but not limited to, computer network, data network, and network. The network allows computing devices 700 to exchange data using connections, which may be known to a person having ordinary skill in the art as data links, between network nodes. The nodes comprise network computer devices 700 that originate, route, and terminate data. The nodes are identified by network addresses and can include a plurality of hosts consistent with the embodiments of a computing device 700. The aforementioned embodiments include, but not limited to personal computers, phones, servers, drones, and networking devices such as, but not limited to, hubs, switches, routers, modems, and firewalls.

Two nodes can be said are networked together, when one computing device 700 is able to exchange information with the other computing device 700, whether or not they have a direct connection with each other. The communication sub-module 762 supports a plurality of applications and services, such as, but not limited to World Wide Web (WWW), digital video and audio, shared use of application and storage computing devices 700, printers/scanners/fax machines, email/online chat/instant messaging, remote control, distributed computing, etc. The network may comprise a plurality of transmission mediums, such as, but not limited to conductive wire, fiber optics, and wireless. The network may comprise a plurality of communications protocols to organize network traffic, wherein application-specific communications protocols are layered, may be known to a person having ordinary skill in the art as carried as payload, over other more general communications protocols. The plurality of communications protocols may comprise, but not limited to, IEEE 802, ethernet, Wireless LAN (WLAN/Wi-Fi), Internet Protocol (IP) suite (e.g., TCP/IP, UDP, Internet Protocol version 4 [Ipv4], and Internet Protocol version 6 [Ipv6]), Synchronous Optical Networking (SONET)/Synchronous Digital Hierarchy (SDH), Asynchronous Transfer Mode (ATM), and cellular standards (e.g., Global System for Mobile Communications [GSM], General Packet Radio Service [GPRS], Code-Division Multiple Access [CDMA], and Integrated Digital Enhanced Network [IDEN]).

The communication sub-module 762 may comprise a plurality of size, topology, traffic control mechanism and organizational intent. The communication sub-module 762 may comprise a plurality of embodiments, such as, but not limited to:

-   -   Wired communications, such as, but not limited to, coaxial         cable, phone lines, twisted pair cables (ethernet), and         InfiniBand.     -   Wireless communications, such as, but not limited to,         communications satellites, cellular systems, radio         frequency/spread spectrum technologies, IEEE 802.11 Wi-Fi,         Bluetooth, NFC, free-space optical communications, terrestrial         microwave, and Infrared (IR) communications. Wherein cellular         systems embody technologies such as, but not limited to, 3G,4G         (such as WiMax and LTE), and 5G (short and long wavelength).     -   Parallel communications, such as, but not limited to, LPT ports.     -   Serial communications, such as, but not limited to, RS-232 and         USB.     -   Fiber Optic communications, such as, but not limited to,         Single-mode optical fiber (SMF) and Multi-mode optical fiber         (MMF).     -   Power Line communications

The aforementioned network may comprise a plurality of layouts, such as, but not limited to, bus network such as ethernet, star network such as Wi-Fi, ring network, mesh network, fully connected network, and tree network. The network can be characterized by its physical capacity or its organizational purpose. Use of the network, including user authorization and access rights, differ accordingly. The characterization may include, but not limited to nanoscale network, Personal Area Network (PAN), Local Area Network (LAN), Home Area Network (HAN), Storage Area Network (SAN), Campus Area Network (CAN), backbone network, Metropolitan Area Network (MAN), Wide Area Network (WAN), enterprise private network, Virtual Private Network (VPN), and Global Area Network (GAN).

Consistent with the embodiments of the present disclosure, the aforementioned computing device 700 may employ the sensors sub-module 763 as a subset of the I/O 760. The sensors sub-module 763 comprises at least one of the devices, modules, and subsystems whose purpose is to detect events or changes in its environment and send the information to the computing device 700. Sensors are sensitive to the measured property, are not sensitive to any property not measured, but may be encountered in its application, and do not significantly influence the measured property. The sensors sub-module 763 may comprise a plurality of digital devices and analog devices, wherein if an analog device is used, an Analog to Digital (A-to-D) converter must be employed to interface the said device with the computing device 700. The sensors may be subject to a plurality of deviations that limit sensor accuracy. The sensors sub-module 763 may comprise a plurality of embodiments, such as, but not limited to, chemical sensors, automotive sensors, acoustic/sound/vibration sensors, electric current/electric potential/magnetic/radio sensors, environmental/weather/moisture/humidity sensors, flow/fluid velocity sensors, ionizing radiation/particle sensors, navigation sensors, position/angle/displacement/distance/speed/acceleration sensors, imaging/optical/light sensors, pressure sensors, force/density/level sensors, thermal/temperature sensors, and proximity/presence sensors. It should be understood by a person having ordinary skill in the art that the ensuing are non-limiting examples of the aforementioned sensors:

-   -   Chemical sensors, such as, but not limited to, breathalyzer,         carbon dioxide sensor, carbon monoxide/smoke detector, catalytic         bead sensor, chemical field-effect transistor, chemiresistor,         electrochemical gas sensor, electronic nose,         electrolyte-insulator-semiconductor sensor, energy-dispersive         X-ray spectroscopy, fluorescent chloride sensors, holographic         sensor, hydrocarbon dew point analyzer, hydrogen sensor,         hydrogen sulfide sensor, infrared point sensor, ion-selective         electrode, nondispersive infrared sensor, microwave chemistry         sensor, nitrogen oxide sensor, olfactometer, optode, oxygen         sensor, ozone monitor, pellistor, pH glass electrode,         potentiometric sensor, redox electrode, zinc oxide nanorod         sensor, and biosensors (such as nanosensors).     -   Automotive sensors, such as, but not limited to, air flow         meter/mass airflow sensor, air-fuel ratio meter, AFR sensor,         blind spot monitor, engine coolant/exhaust gas/cylinder         head/transmission fluid temperature sensor, hall effect sensor,         wheel/automatic transmission/turbine/vehicle speed sensor,         airbag sensors, brake fluid/engine crankcase/fuel/oil/tire         pressure sensor, camshaft/crankshaft/throttle position sensor,         fuel/oil level sensor, knock sensor, light sensor, MAP sensor,         oxygen sensor (o2), parking sensor, radar sensor, torque sensor,         variable reluctance sensor, and water-in-fuel sensor.     -   Acoustic, sound and vibration sensors, such as, but not limited         to, microphone, lace sensor (guitar pickup), seismometer, sound         locator, geophone, and hydrophone.     -   Electric current, electric potential, magnetic, and radio         sensors, such as, but not limited to, current sensor, Daly         detector, electroscope, electron multiplier, faraday cup,         galvanometer, hall effect sensor, hall probe, magnetic anomaly         detector, magnetometer, magnetoresistance, MEMS magnetic field         sensor, metal detector, planar hall sensor, radio direction         finder, and voltage detector.     -   Environmental, weather, moisture, and humidity sensors, such as,         but not limited to, actinometer, air pollution sensor,         bedwetting alarm, ceilometer, dew warning, electrochemical gas         sensor, fish counter, frequency domain sensor, gas detector,         hook gauge evaporimeter, humistor, hygrometer, leaf sensor,         lysimeter, pyranometer, pyrgeometer, psychrometer, rain gauge,         rain sensor, seismometers, SNOTEL, snow gauge, soil moisture         sensor, stream gauge, and tide gauge.     -   Flow and fluid velocity sensors, such as, but not limited to,         air flow meter, anemometer, flow sensor, gas meter, mass flow         sensor, and water meter.     -   Ionizing radiation and particle sensors, such as, but not         limited to, cloud chamber, Geiger counter, Geiger-Muller tube,         ionization chamber, neutron detection, proportional counter,         scintillation counter, semiconductor detector, and         thermoluminescent dosimeter.     -   Navigation sensors, such as, but not limited to, air speed         indicator, altimeter, attitude indicator, depth gauge, fluxgate         compass, gyroscope, inertial navigation system, inertial         reference unit, magnetic compass, MHD sensor, ring laser         gyroscope, turn coordinator, variometer, vibrating structure         gyroscope, and yaw rate sensor.     -   Position, angle, displacement, distance, speed, and acceleration         sensors, such as, but not limited to, accelerometer,         displacement sensor, flex sensor, free fall sensor, gravimeter,         impact sensor, laser rangefinder, LIDAR, odometer, photoelectric         sensor, position sensor such as, but not limited to, GPS or         Glonass, angular rate sensor, shock detector, ultrasonic sensor,         tilt sensor, tachometer, ultra-wideband radar, variable         reluctance sensor, and velocity receiver.     -   Imaging, optical and light sensors, such as, but not limited to,         CMOS sensor, colorimeter, contact image sensor, electro-optical         sensor, infra-red sensor, kinetic inductance detector, LED as         light sensor, light-addressable potentiometric sensor, Nichols         radiometer, fiber-optic sensors, optical position sensor,         thermopile laser sensor, photodetector, photodiode,         photomultiplier tubes, phototransistor, photoelectric sensor,         photoionization detector, photomultiplier, photoresistor,         photoswitch, phototube, scintillometer, Shack-Hartmann,         single-photon avalanche diode, superconducting nanowire         single-photon detector, transition edge sensor, visible light         photon counter, and wavefront sensor.     -   Pressure sensors, such as, but not limited to, barograph,         barometer, boost gauge, bourdon gauge, hot filament ionization         gauge, ionization gauge, McLeod gauge, Oscillating U-tube,         permanent downhole gauge, piezometer, Pirani gauge, pressure         sensor, pressure gauge, tactile sensor, and time pressure gauge.     -   Force, Density, and Level sensors, such as, but not limited to,         bhangmeter, hydrometer, force gauge or force sensor, level         sensor, load cell, magnetic level or nuclear density sensor or         strain gauge, piezocapacitive pressure sensor, piezoelectric         sensor, torque sensor, and viscometer.     -   Thermal and temperature sensors, such as, but not limited to,         bolometer, bimetallic strip, calorimeter, exhaust gas         temperature gauge, flame detection/pyrometer, Gardon gauge,         Golay cell, heat flux sensor, microbolometer, microwave         radiometer, net radiometer, infrared/quartz/resistance         thermometer, silicon bandgap temperature sensor, thermistor, and         thermocouple.     -   Proximity and presence sensors, such as, but not limited to,         alarm sensor, doppler radar, motion detector, occupancy sensor,         proximity sensor, passive infrared sensor, reed switch, stud         finder, triangulation sensor, touch switch, and wired glove.

Consistent with the embodiments of the present disclosure, the aforementioned computing device 700 may employ the peripherals sub-module 762 as a subset of the I/O 760. The peripheral sub-module 764 comprises ancillary devices uses to put information into and get information out of the computing device 700. There are 3 categories of devices comprising the peripheral sub-module 764, which exist based on their relationship with the computing device 700, input devices, output devices, and input/output devices. Input devices send at least one of data and instructions to the computing device 700. Input devices can be categorized based on, but not limited to:

-   -   Modality of input, such as, but not limited to, mechanical         motion, audio, visual, and tactile.     -   Whether the input is discrete, such as but not limited to,         pressing a key, or continuous such as, but not limited to         position of a mouse.     -   The number of degrees of freedom involved, such as, but not         limited to, two-dimensional mice vs three-dimensional mice used         for Computer-Aided Design (CAD) applications.

Output devices provide output from the computing device 700. Output devices convert electronically generated information into a form that can be presented to humans. Input/output devices perform that perform both input and output functions. It should be understood by a person having ordinary skill in the art that the ensuing are non-limiting embodiments of the aforementioned peripheral sub-module 764:

-   -   Input Devices         -   Human Interface Devices (HID), such as, but not limited to,             pointing device (e.g., mouse, touchpad, joystick,             touchscreen, game controller/gamepad, remote, light pen,             light gun, Wii remote, jog dial, shuttle, and knob),             keyboard, graphics tablet, digital pen, gesture recognition             devices, magnetic ink character recognition, Sip-and-Puff             (SNP) device, and Language Acquisition Device (LAD).         -   High degree of freedom devices, that require up to six             degrees of freedom such as, but not limited to, camera             gimbals, Cave Automatic Virtual Environment (CAVE), and             virtual reality systems.         -   Video Input devices are used to digitize images or video             from the outside world into the computing device 700. The             information can be stored in a multitude of formats             depending on the user's requirement. Examples of types of             video input devices include, but not limited to, digital             camera, digital camcorder, portable media player, webcam,             Microsoft Kinect, image scanner, fingerprint scanner,             barcode reader, 3D scanner, laser rangefinder, eye gaze             tracker, computed tomography, magnetic resonance imaging,             positron emission tomography, medical ultrasonography, TV             tuner, and iris scanner.         -   Audio input devices are used to capture sound. In some             cases, an audio output device can be used as an input             device, in order to capture produced sound. Audio input             devices allow a user to send audio signals to the computing             device 700 for at least one of processing, recording, and             carrying out commands. Devices such as microphones allow             users to speak to the computer in order to record a voice             message or navigate software. Aside from recording, audio             input devices are also used with speech recognition             software. Examples of types of audio input devices include,             but not limited to microphone, Musical Instrumental Digital             Interface (MIDI) devices such as, but not limited to a             keyboard, and headset.         -   Data AcQuisition (DAQ) devices covert at least one of analog             signals and physical parameters to digital values for             processing by the computing device 700. Examples of DAQ             devices may include, but not limited to, Analog to Digital             Converter (ADC), data logger, signal conditioning circuitry,             multiplexer, and Time to Digital Converter (TDC).     -   Output Devices may further comprise, but not be limited to:         -   Display devices, which convert electrical information into             visual form, such as, but not limited to, monitor, TV,             projector, and Computer Output Microfilm (COM). Display             devices can use a plurality of underlying technologies, such             as, but not limited to, Cathode-Ray Tube (CRT), Thin-Film             Transistor (TFT), Liquid Crystal Display (LCD), Organic             Light-Emitting Diode (OLED), MicroLED, E Ink Display             (ePaper) and Refreshable Braille Display (Braille Terminal).         -   Printers, such as, but not limited to, inkjet printers,             laser printers, 3D printers, solid ink printers and             plotters.         -   Audio and Video (AV) devices, such as, but not limited to,             speakers, headphones, amplifiers and lights, which include             lamps, strobes, DJ lighting, stage lighting, architectural             lighting, special effect lighting, and lasers.         -   Other devices such as Digital to Analog Converter (DAC).     -   Input/Output Devices may further comprise, but not be limited         to, touchscreens, networking device (e.g., devices disclosed in         network 762 sub-module), data storage device (non-volatile         storage 761), facsimile (FAX), and graphics/sound cards. 

The following is claimed:
 1. A payload deployment mechanism, comprising: a body portion; a bay area partially defined by the body portion; a configurable payload operative to detachably connect to the body portion of the payload deployment mechanism; a force generating mechanism attached to the payload deployment mechanism, the force generating mechanism configured to impart force to the configurable payload to separate the configurable payload from the payload deployment mechanism; and a hinge mechanism configured to control the separation of the configurable payload from the payload deployment mechanism, the hinge mechanism being configured to pivot about a pivot point located external to the payload deployment mechanism.
 2. The payload deployment mechanism of claim 1, wherein the payload deployment mechanism is configured to retain the configurable payload by at least one latch assembly comprising at least one biasing mechanism.
 3. The payload deployment mechanism of claim 1, wherein the configurable payload is shaped to generate drag and create additional force to detach the configurable payload from the payload deployment mechanism as it separates from the payload deployment mechanism.
 4. The payload deployment mechanism of claim 3, wherein the configurable payload comprises at least one of a forward edge of the configurable payload or a side portion of the configurable payload configured to generate the drag.
 5. The payload deployment mechanism of claim 3, wherein the configurable payload is integrated into the payload deployment mechanism without affect to aerodynamics of the payload deployment mechanism while attached to the payload deployment mechanism.
 6. The payload deployment mechanism of claim 3, wherein the generated drag from the configurable payload causes separation of the configurable payload from the payload deployment mechanism.
 7. The payload deployment mechanism of claim 1, further comprising at least one vent configured to direct external airflow into the payload deployment mechanism.
 8. The payload deployment mechanism of claim 7, wherein the at least one vent directs the external airflow into the payload deployment mechanism to equalize air with external air pressure as the configurable payload separates form the payload deployment mechanism.
 9. The payload deployment mechanism of claim 1, wherein the hinge mechanism comprises a first hinge component and a second hinge component.
 10. The payload deployment mechanism of claim 9, wherein the first hinge component on the payload deployment mechanism and the second hinge component on the configurable payload separate to deploy the configurable payload.
 11. The payload deployment mechanism of claim 1, wherein the hinge mechanism is located at an aft end of the configurable payload.
 12. The payload deployment mechanism of claim 1, further comprising a parachute attached to the configurable payload.
 13. The payload deployment mechanism of claim 12, wherein the parachute is disposed within the payload deployment mechanism before deployment.
 14. The payload deployment mechanism of claim 12, wherein the parachute is configured to deploy due to the separation of the configurable payload from the payload deployment mechanism.
 15. The payload deployment mechanism of claim 12, wherein the parachute is a static line parachute.
 16. The payload deployment mechanism of claim 1, wherein the hinge mechanism is configured to prevent the configurable payload from contacting the payload deployment mechanism after separation of the configurable payload from the payload deployment mechanism.
 17. The payload deployment mechanism of claim 1, wherein the payload deployment mechanism is incorporated into an aerial vehicle.
 18. The payload deployment mechanism of claim 1, wherein the payload deployment mechanism is configured to be connected to an aircraft by a coupling assembly arranged between the payload deployment mechanism and a portion of the aircraft.
 19. The payload deployment mechanism of claim 1, wherein the bay area is partially defined by a cavity in the payload deployment mechanism.
 20. The payload deployment mechanism of claim 1, wherein the configurable payload comprises one or more of: a drone, a sensor, a buoy, a munition, an unmanned aerial vehicle, or an object suitable for deployment from within the payload deployment mechanism. 